EP4116560A1 - Anzapfluftabsaugvorrichtung für ein gasturbinentriebwerk - Google Patents

Anzapfluftabsaugvorrichtung für ein gasturbinentriebwerk Download PDF

Info

Publication number
EP4116560A1
EP4116560A1 EP22183184.5A EP22183184A EP4116560A1 EP 4116560 A1 EP4116560 A1 EP 4116560A1 EP 22183184 A EP22183184 A EP 22183184A EP 4116560 A1 EP4116560 A1 EP 4116560A1
Authority
EP
European Patent Office
Prior art keywords
duct
offtake
line
gas turbine
turbine engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
EP22183184.5A
Other languages
English (en)
French (fr)
Inventor
Eric Durocher
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of EP4116560A1 publication Critical patent/EP4116560A1/de
Pending legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/145—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path by means of valves, e.g. for steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/231—Three-dimensional prismatic cylindrical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/606—Bypassing the fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/60—Control system actuates means
    • F05D2270/65—Pneumatic actuators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the application relates generally to aircraft engines and, more particularly, to turbine engines having bleed air systems.
  • Bleed air is provided by a gas turbine engine to be used for engine functions (such as cooling of turbines and to help seal bearing cavities, for example) and, as the case may be, for aircraft functions (such as wing de-icing, cabin pressurization, cabin climate control, liquid tank pressurization, etc.).
  • engine functions such as cooling of turbines and to help seal bearing cavities, for example
  • aircraft functions such as wing de-icing, cabin pressurization, cabin climate control, liquid tank pressurization, etc.
  • bleed air can be derived from an air intake duct or compressor cavity. While typical conventional bleed air systems may be suitable for their intended purposes, aerodynamics and/or performance of such existing systems may nevertheless be improved upon.
  • a gas turbine engine comprising: a duct extending about an axis, the duct including an outer-duct wall having an interior-duct surface circumscribing an interior of the duct and an exterior-duct surface radially outward of the interior-duct surface relative to the axis, the outer-duct wall defining an offtake opening extending from the interior-duct surface to the exterior-duct surface, the offtake opening in fluid communication between an offtake location inside the duct and outside the duct, and a bleed air offtake assembly including: an air line in fluid communication with inside the duct via the offtake opening, the air line having a first-line end defining a line inlet proximate to the outer-duct wall and a second-line end spaced from the first-line end; a valve located outside the duct and fluidly connected to the air line via the second-line end, and a conduit having a conduit inlet in fluid communication with inside the air line at a resonance location between the first-line end and the second
  • the outer-duct wall defines a relief opening extending from the interior-duct surface to the exterior-duct surface, and the conduit outlet is in fluid communication with inside the duct via the relief opening.
  • the relief opening includes a plurality of bores.
  • the conduit is located inside the air line.
  • the bleed air offtake assembly includes a tube extending from the exterior-duct surface to the resonance location inside the air line, the tube having an exterior-tube surface, the air line has an interior-line surface surrounding the exterior-tube surface, and the conduit has an annular shape circumscribed inwardly by the exterior-tube surface and outwardly by the interior-line surface.
  • a portion of the tube and a portion of the air line have cylindrical shapes that are coaxial to one another.
  • the tube defines at least one lateral opening in fluid communication between inside the tube and inside the conduit.
  • the outer-duct wall defines a relief opening extending from the interior-duct surface to the exterior-duct surface, the relief opening surrounded by the line inlet, and the bleed air offtake assembly includes a tube having an interior defining the conduit and opposite ends respectively defining the conduit inlet and the conduit outlet, the conduit outlet in fluid communication with inside the duct via the relief opening.
  • the outer-duct wall has a boss projecting into the duct, the boss defining the offtake opening and a relief opening, the conduit outlet in fluid communication with inside the duct via the relief opening.
  • the boss has a fore-facing side defining the offtake opening and an aft-facing side defining the relief opening.
  • the conduit is located outside the air line, the bleed air offtake assembly including a tube having an interior defining the conduit and opposite ends respectively defining the conduit inlet and the conduit outlet.
  • the gas turbine engine is a turbofan gas turbine engine and the duct is a bypass duct.
  • the duct has a duct inlet upstream of the offtake opening and the relief location is downstream of the offtake location relative to the duct inlet.
  • the gas turbine engine is a turboshaft gas turbine engine having a first stage compressor and a second stage compressor downstream of the first stage compressor, and the duct defines a bleed air cavity of the second stage compressor.
  • the gas turbine engine is a turboprop gas turbine engine having a compressor and the duct defines a bleed air cavity of the compressor.
  • a gas turbine engine comprising: a duct extending about an axis, the duct including an outer-duct wall having an interior-duct surface circumscribing an interior of the duct and an exterior-duct surface radially outward of the interior-duct surface relative to the axis, the outer-duct wall defining an offtake opening extending from the interior-duct surface to the exterior-duct surface, the offtake opening in fluid communication between inside the duct and outside the duct, and a bleed air offtake assembly including: an air line in fluid communication with inside the duct via the offtake opening, the air line having a first-line end defining a line inlet proximate to the outer-duct wall and a second-line end spaced from the first-line end; a valve located outside the duct and fluidly connected to the air line via the second-line end, and a tube extending from the exterior-duct surface to a resonance location inside the air line, the tube having an exterior-tube surface surrounded by an interior-
  • the tube has a proximal-tube end surrounding the offtake opening, the outer-duct wall defines a relief opening spaced from the proximal-tube end, and the line inlet surrounds the proximal-tube end and the relief opening.
  • the outer-duct wall defines a boss projecting into the duct, the offtake opening is defined in a fore-facing side of the boss and the relief opening is defined in an aft-facing side of the boss.
  • the relief opening includes a plurality of bores.
  • the plurality of bores are distributed around the proximal-tube end.
  • Fig.1A illustrates a gas turbine engine 10A being of a turbofan type preferably provided for use in an aircraft for subsonic flight, generally comprising in serial flow communication along a centerline CL a fan 12 through which ambient air is propelled, a compressor section 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
  • the compressor section 14 and the turbine section 18 form part of an engine core 20.
  • the engine core 20 defines a main fluid path 22 in which the combustor 16 is provided.
  • the engine core 20 has an annular wall facing radially outwardly relative to the centerline CL, referred to as a core wall 24.
  • the core wall 24 is positioned coaxially and radially inwardly of a nacelle 26 of the engine 10A.
  • the nacelle 26 has an annular wall facing radially inwardly relative to the centerline CL, referred to as an engine wall 28.
  • the core wall 24 and the engine wall 28 together define an annular bypass duct 30 for directing an air flow F (the flow F) drawn by the fan 12 such that the flow F bypasses the main fluid path 22.
  • the core wall 24 and the engine wall 28 can also be respectively referred to as inner and outer walls of the duct 30.
  • a bleed air offtake assembly 40 (the offtake assembly 40) is fluidly connected to the duct 30 such that some of the air flow F may be drawn from the duct 30 by the offtake assembly 40 to drive and/or supply one or more pneumatically-driven aircraft systems 50 connected thereto. Stated otherwise, the offtake assembly 40 is operatively connected to the duct 30. In this case, the offtake assembly 40 is connected to an annular outer-duct wall 32 (the outer-duct wall 32) of the duct 30 being a portion of the engine wall 28 spaced aft from an inlet of the duct 30.
  • the outer-duct wall 32 to which the offtake assembly 40 is located can be located between a fan outer bypass vane and a bypass air-exhaust gas mixer of the engine 10.
  • the offtake assembly 40 generally includes an air line 60 (the line 60) having a first-line end defining a line inlet 62 in fluid communication with inside the duct 30 via the outer-duct wall 32 and a second-line end opposite the first-line end, a valve 70 located outside the duct 30 and fluidly connected to the line 60 via the second-line end, and a pressure-relief conduit 80 (the conduit 80, Fig. 2 ) having opposite ends respectively in fluid communication with inside the line 60, at a location between the first-line end and the second-line end upstream of the valve 70, and with inside the duct 30.
  • the valve 70 is fluidly connected between the line 60 and a pre-cooler being a part of the one or more aircraft systems 50.
  • the offtake assembly 40 may be employed with any other suitable engine type and at any suitable location thereof. For instance, referring to Fig. 1B , another gas turbine engine 10B is shown.
  • the engine 10B is a turboshaft engine generally comprising in serial flow communication a low pressure compressor section (or first stage compressor) 12B and a high pressure compressor section (or second stage compressor) 14B for pressurizing air, a combustor 16B in which the compressed air is mixed with a fuel flow delivered to the combustor 16B via fuel nozzles of a fuel system (not depicted) and ignited for generating a stream of hot combustion gases, a high pressure turbine section 18B for extracting energy from the combustion gases and driving the high pressure compressor section 14B via a high pressure shaft 20B, and a low pressure turbine section 22B for further extracting energy from the combustion gases and driving the low pressure compressor section 12B via a low pressure shaft 24B.
  • the offtake assembly 40 is operatively connected to a duct or air plenum 30B defining a compressor bleed cavity of the high pressure compressor section 14B.
  • the engine 10C is a turboprop engine generally comprising in serial flow communication an air inlet 12C through which ambient air enters the engine, a compressor section 14C for pressurizing the air, a combustor 16C in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18C for extracting energy from the combustion gases.
  • the turbine section 18C includes a compressor turbine section 20C driving the rotor(s) of the compressor section 14C through a compressor shaft 22C, and a free power turbine section 24C driving a propeller 26C through a power shaft 28C.
  • the offtake assembly 40 is operatively connected to a duct or air plenum 30C defining a compressor bleed cavity of the compressor section 14C.
  • Fig. 2 portions of the offtake assembly 40 proximate to the outer-duct wall 32 are shown, including a portion of the line 60 having the line inlet 62 and including the conduit 80, whereas the valve 70 and a portion of the line 60 proximate to the valve 70 have been removed.
  • the line 60 is a tubular structure which, in this embodiment, features the line inlet 62 having a cylindrical shape projecting outwardly from an exterior-duct surface 32e of the outer-duct wall 32.
  • the line 60 extends from line inlet 62 at an angle ⁇ to the exterior-duct surface 32e so as to be inclined relative to the flow F.
  • the line 60 can be inclined rearwardly (i.e., cocurrent relative to the flow F), at a right angle or forwardly (i.e., crosscurrent relative to the flow F).
  • Other shapes and orientations for the line inlet 62 are possible, so long as suitable aerodynamics are attained.
  • the flow F must be partially drawn into the line 60 from inside the duct 30 such that a bleed air flow Fb (the bleed flow Fb, Fig. 3 ) having suitable aerodynamic properties is delivered to the valve 70.
  • the line 60 is in fluid communication with an offtake location L1 inside the duct 30 via an offtake opening 34 defined through the outer-duct wall 32.
  • the offtake opening 34 extends from an interior-duct surface 32i ( Fig. 3 ) of the outer-duct wall 32 to the exterior-duct surface 32e.
  • the offtake location L1 adjoins a fore, high-pressure side of the offtake opening 34.
  • the outer-duct wall 32 has a boss 36 projecting into the duct 30.
  • the offtake opening 34 is defined at least partially onto an upstream, fore-facing side of the boss 36 such that the offtake opening 34 at least partially faces the flow F.
  • the boss 36 and the offtake opening 34 are arranged relative to the interior-duct surface 32i such that as the flow F runs along the interior-duct surface 32i at the offtake location L1, a portion of the flow F is incident relative to the offtake opening 34.
  • the line inlet 62 is joined to the exterior-duct surface 32e so as to surround the offtake opening 34, forming a seal therewith preventing air entering the offtake opening 34 from bypassing the line 60.
  • the conduit 80 is provided in the form of an elongated volume partitioned inside the line 60.
  • the conduit 80 has opposite open ends, respectively a conduit inlet 82 in fluid communication with a resonance location L2 inside the line 60 distanced from both the line inlet 62 and the valve 70, and a conduit outlet 84 in fluid communication with a relief location L3 ( Fig. 3 ) inside the duct 30.
  • the relief location L3 adjoins an aft, low-pressure side of the offtake opening 34.
  • the relief location L3 is thus located aft of the offtake location L1, although it does not have to be the case, as will be explained hereinbelow.
  • a tube 90 of the offtake assembly 40 is received inside the line 60 in an overlaid yet spaced positioning relative to the line 60.
  • the line 60 surrounds the tube 90 as the line 60 extends away from the exterior-duct surface 32e so as to define the conduit 80 between an interior-line surface 60i of the line 60 and an exterior-tube surface 90e of the tube 90.
  • a distal-tube end 92 of the tube 90 is located at the resonance location L2 and is surrounded by the interior-line surface 60i.
  • a proximal-tube end 94 of the tube 90 opposite the distal-tube end 92 is joined to the exterior-duct surface 32e so as to follow a periphery of the offtake opening 34 and be surrounded by the interior-line surface 60i.
  • the proximal-tube end 94 forms a seal with the exterior-duct surface 32e proximate to the periphery of the offtake opening 34, forcing air having exited the duct 30 via the offtake opening 34 to travel through the tube 90 before it may pressurize the line 60 at the resonance location L2 and enter the conduit 80.
  • an exterior-tube surface 90e of the tube 90 defines an inner boundary of the conduit inlet 82.
  • the exterior-tube surface 90e defines an inner boundary of the conduit outlet 84.
  • Outer boundaries of the conduit inlet 82 and conduit outlet 84 are respectively defined by the interior-line surface 60i.
  • the line 60 and the tube 90 are shaped and positioned relative to one another such that a portion of the conduit 80 located at the resonance location L2 is annular in shape.
  • the line 60 and the tube 90 respectively have cylindrical shapes that are coaxial to one another.
  • other shapes are contemplated, insofar as the conduit 80 forms a fluid passage from the conduit inlet 82 to the conduit outlet 84 for a relief flow Fr to travel via the conduit 80 from the resonance location L2 to the relief location L3.
  • the line 60 and the tube 90 may be routed so as to follow different paths as they extend outward of the duct 30, imparting the conduit 80 with a non necessarily annular shape.
  • one of the line 60 and the tube 90 may follow a straight path and the other a curvilinear path.
  • One or both of the line 60 and the tube 90 may have a non-circular cross-section.
  • the line 60 and the tube 90 may be constructed of composite and/or metallic materials, such as stainless steel or titanium.
  • the line 60 is constructed of a metallic material suitable for withstanding high temperatures and for shielding the tube 90 from such high temperatures.
  • the tube 90 is constructed of a composite material.
  • the line 60 and the tube 90 are constructed of composite materials.
  • the conduit 80 is in fluid communication with the relief location L3 inside the duct 30 via a relief opening 38 defined through the outer-duct wall 32 from the exterior-duct surface 32e to the interior-duct surface 32i.
  • the relief opening 38 is provided in the form of a plurality of bores 38A positioned so as to be in communication between the conduit outlet 84 and the relief location L3.
  • the bores 38A are distributed arcuately next to one another peripherally to the proximate-tube end 94 and so as to be surrounded by the line inlet 62.
  • Such a multi-opening arrangement for the relief opening 38 can advantageously assist the relief flow Fr from migrating from inside the conduit 80 to inside the duct 30 while maintaining the structural integrity of the duct 30.
  • the relief opening 38 is defined at least partially onto a downstream, aft-facing side of the boss 36 so as to direct the relief flow Fr concurrently to the flow F away from the offtake opening 34.
  • Other shapes and spatial arrangements for the relief opening 38 are possible.
  • the air flow F flows inside the duct 30 from the inlet to the offtake location L1 on the high-pressure side of the offtake opening 34, and supplies the bypass flow Fb into the offtake assembly 40.
  • flow separation and vortex shedding of the bypass flow Fb occur proximate to the line inlet 62, leading to cyclical pressurization (i.e., pressure amplitude spikes, or dashes) inside the line 60 upon the valve 70 being closed.
  • cyclical pressurization i.e., pressure amplitude spikes, or dashes
  • the resonance location L2 encompasses a portion of the interior line surface 60i most solicited by the pressurization, and is referred to as such due to the vibration of the line 60 and resulting acoustic tones emitted thereby under certain operating conditions of the engine 10A.
  • the tube 90 is sized and arranged such that the conduit 80 extends to the resonance location L2, i.e., the conduit inlet 82 is located proximate to the resonance location L2.
  • the pressure building up at the resonance location L2 is maintained under a certain desired maximum level, or built-up pressure, by allowing pressure in excess of the built-up pressure to be relieved via the conduit 30.
  • the line 60 is sized and arranged relative to the duct inlet such that upon the duct 30 being at an intake pressure at the duct inlet and the valve 70 being closed, an offtake pressure at the offtake location L1 is less than the intake pressure, and built up pressure at the resonance location L2 is greater than the offtake pressure.
  • the built up pressure at the resonance location L2 is greater than a relief pressure inside the duct 30 at the relief location L3. This creates a positive pressure differential between inside the line 60 at the resonance location L2 and inside the duct 30 at the relief location L3, allowing the relief of the excess pressure to occur via the conduit 80. It should be noted that the built up pressure is also greater than an offtake pressure inside the duct 30 at the offtake location L1.
  • the relief location L3 and the offtake location L1 may be at a same distance from the inlet, or the relief location L3 may even be upstream of the offtake location L1, so long as a suitable positive pressure differential is attained.
  • the resonance location L2 is at a pressure that is less than inside the duct 30 at either the offtake location L1 or the relief location L3.
  • FIG. 5 there is shown another embodiment of the offtake assembly 40 in which the tube 90 has lateral openings 96 extending from an interior-tube surface 90i of the tube 90 to the exterior-tube surface 90e so as to be in fluid communication between inside the tube 90 and inside the conduit 80.
  • the lateral openings 96 are positioned at or proximate to the resonance location L2 inside the line 60.
  • Quantity, size, shape (e.g., bore(s), slot(s)), and spatial arrangement of such lateral openings 96 are determined with respect to high pressure amplitude areas of the resonance location L2 so as to assist migration of the bleed flow Fb away from the resonance location L2 via the conduit 80 and thereby assist migration of the relief flow Fr from inside of the conduit 80 to inside of the duct 30.
  • a density of the lateral openings 96 varies along the length of the tube 90, and is greatest alongside a portion of the resonance location L2 being the closest to the conduit inlet 82. The density of the lateral openings 96 increases along the tube 90 toward the distal-tube end 92.
  • the line inlet 62 flares as it meets the boss 36 near a periphery thereof so as to surround the proximal-tube end 94 as well as the relief opening 38.
  • the boss 36, the line inlet 62 and the proximal-tube end 94 can be shaped such that the conduit 80 increases in size as it nears the conduit outlet 84, and thus can advantageously allow to optimize the configuration of the relief opening 38.
  • a plurality of openings 38A can be distributed next to one another, for example radially outwardly relative to the offtake opening 34.
  • Fig. 6 yet another embodiment of the offtake assembly 40 is shown, in which the conduit 80 is alternatively formed by an interior of the tube 90.
  • the proximal-tube end 94 defines the conduit outlet 34, and meets the outer-duct wall 32 so as to follow a periphery of the relief opening 38.
  • the distal-tube end defines the conduit inlet 82.
  • FIG. 7 to 9 there is shown yet another embodiment of the offtake assembly 40, in which the conduit 80 is formed by an interior of a tube 100 provided outside the line 60.
  • a distal end 102 of the tube 100 which defines the conduit inlet 82, is fluidly connected to the line 60 at the resonance location L2.
  • a proximal end 104 of the tube 100 defines the conduit outlet 84 and is fluidly connected to the relief opening 38 in the duct 30 such that the resonance location L2 inside the line 60 is in fluid communication with inside the duct 30.
  • the relief opening 38 is located proximate to the offtake opening 34 and the tube 100 runs alongside the line 60.
  • the relief opening 38 may be defined in the outer-duct wall 32 at a location remote from the offtake opening 34, for example further downstream and away from the boss 36, or even upstream of the offtake opening 34, so long as a suitable pressure differential is attainable between inside the line 60 at the resonance location L2 and inside the duct 30 at the location of the relief opening 38.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP22183184.5A 2021-07-06 2022-07-05 Anzapfluftabsaugvorrichtung für ein gasturbinentriebwerk Pending EP4116560A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US17/367,774 US11732645B2 (en) 2021-07-06 2021-07-06 Bleed air offtake assembly for a gas turbine engine

Publications (1)

Publication Number Publication Date
EP4116560A1 true EP4116560A1 (de) 2023-01-11

Family

ID=82558005

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22183184.5A Pending EP4116560A1 (de) 2021-07-06 2022-07-05 Anzapfluftabsaugvorrichtung für ein gasturbinentriebwerk

Country Status (3)

Country Link
US (1) US11732645B2 (de)
EP (1) EP4116560A1 (de)
CA (1) CA3166771A1 (de)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2022136835A (ja) * 2021-03-08 2022-09-21 日本電産株式会社 回転電機、および駆動装置

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100126182A1 (en) * 2008-11-21 2010-05-27 Honeywell International Inc. Flush inlet scoop design for aircraft bleed air system
EP3163054A1 (de) * 2015-11-02 2017-05-03 General Electric Company Verfahren und system zur abschwächung von hohlraumresonanzen
CN110439692A (zh) * 2019-08-19 2019-11-12 中国商用飞机有限责任公司 发动机风扇进气入口装置

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6438941B1 (en) * 2001-04-26 2002-08-27 General Electric Company Bifurcated splitter for variable bleed flow
US7556223B2 (en) * 2006-12-04 2009-07-07 The Boeing Company Vent system for an aerospace vehicle
US11300002B2 (en) * 2018-12-07 2022-04-12 Pratt & Whitney Canada Corp. Static take-off port

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100126182A1 (en) * 2008-11-21 2010-05-27 Honeywell International Inc. Flush inlet scoop design for aircraft bleed air system
EP3163054A1 (de) * 2015-11-02 2017-05-03 General Electric Company Verfahren und system zur abschwächung von hohlraumresonanzen
CN110439692A (zh) * 2019-08-19 2019-11-12 中国商用飞机有限责任公司 发动机风扇进气入口装置

Also Published As

Publication number Publication date
US20230008514A1 (en) 2023-01-12
CA3166771A1 (en) 2023-01-06
US11732645B2 (en) 2023-08-22

Similar Documents

Publication Publication Date Title
US7549282B2 (en) Multi-slot inter-turbine duct assembly for use in a turbine engine
US6216982B1 (en) Suction device for boundary layer control in an aircraft
US10829232B2 (en) Aircraft comprising a propulsion assembly including a fan on the rear of the fuselage
US7137245B2 (en) High area-ratio inter-turbine duct with inlet blowing
US4999994A (en) Turbo engine
US8876465B2 (en) Gas turbine engine
US8024935B2 (en) Flush inlet scoop design for aircraft bleed air system
US4892269A (en) Spinner ducted exhaust for pusher turboprop engines
US5832715A (en) Small gas turbine engine having enhanced fuel economy
US7658061B2 (en) Gas turbine engine provided with a foreign matter removal passage
US4271666A (en) Integral infrared radiation suppressor for a turbofan engine
EP2685065B1 (de) Propellerluftstrahltriebwerk
US4930725A (en) Pusher propeller installation for turboprop engines
US9644537B2 (en) Free stream intake with particle separator for reverse core engine
US2599879A (en) Exhaust induced cooling system for gas turbines
EP4116560A1 (de) Anzapfluftabsaugvorrichtung für ein gasturbinentriebwerk
CN114991961A (zh) 多流体热交换器
CA2964988C (en) Assembly and method for influencing flow through a fan of a gas turbine engine
US8403629B2 (en) Stator for a jet engine, a jet engine comprising such a stator, and an aircraft comprising the jet engine
EP0440640A1 (de) Nabenhaube mit leitmantel für die abgase eines treibwerks mit schubpropeller
US20090178386A1 (en) Aircraft Propulsion System
US11873737B1 (en) Flow deflector for aperture in gas turbine engine flowpath wall
GB1091621A (en) High efficiency regeneratively cooled gas turbine engines
CN108691654B (zh) 用于备用管理空气系统供能的发动机喷射器的系统和方法
US20240133307A1 (en) Bleed passage arrangement for a gas turbine engine shroud

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20230711

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR